Annotation: The article presents the experience of the first liquid rocket engine parts developing and manufacturing by means of additive technologies. Application of these technologies imposes new constraints on parts configuration, which are necessary to be considered by a designer. At the same time, application of additive technologies provides new opportunities to a developer, which are absent at traditional method of manufacturing. The article presents the results of manufacturing in Yuzhnoye SDO the first commodity parts, manufactured by additive technologies – selective laser melting, using SLM280HL 3D- printer with building volume dimensions of 280x280x350 mm. The obtained experience in the first liquid rocket engine parts developing and manufacturing by means of additive technologies has shown, that application of this technology allows manufacturing the parts having high characteristics at minimum terms and cost of preproduction, however for all potential opportunities realization, especially at implementation phase, it is necessary to change designing philosophy, which will require more working hours at designing. The obtained first results conclusively prove efficiency and expediency of additive technologies application at certain segment of liquid rocket engine parts manufacturing, at that it is clear, that manufacturing equipment improvement and design methods evolution will lead to steady expansion of this segment.

Annotation: The article presents the experience of creating LRE turbopump units by the Rocket Engines Design Office (DO-4) at Yuzhnoye SDO. The best known turbopump units designs developed by DO are described. Both earlier developments of DO and the turbopump unit being now in final testing phase are considered. The design evolution of both separate assemblies and of entire unit is shown. The design evolution allowed increasing the unit’s lifetime dozens times. For example, the lifetime of the first turbopump units developed by DO did not exceed 150 s. Currently, the DO has in stock the engines with lifetime of ~19000 s. The information is presented on the problems that the designers faced in testing the turbopumop unit and the ways to solve them. The unique achievement are presented. At present, there are no analogs of some units in the world. The article presents the information on the latest achievements of DO, such as the face seal on pump vane discs whose use fully excludes unwanted leaks. Having analyzed the data presented, one may conclude that the Rocket Engines Design Office and Yuzhnoye SDO as a whole accumulated sufficient experience and knowledge allowing solving any problems that may arise when developing a new LRE turbopump unit, and successfully operating LRE with turbopump units, including those in the engines with generator gas afterburning created in recent years testify to a great value of accumulated experience.